GB1328540A - Method and devices for the longitudinal stability of helicopters - Google Patents
Method and devices for the longitudinal stability of helicoptersInfo
- Publication number
- GB1328540A GB1328540A GB5528470A GB5528470A GB1328540A GB 1328540 A GB1328540 A GB 1328540A GB 5528470 A GB5528470 A GB 5528470A GB 5528470 A GB5528470 A GB 5528470A GB 1328540 A GB1328540 A GB 1328540A
- Authority
- GB
- United Kingdom
- Prior art keywords
- stabilizer
- helicopter
- flanges
- pivotable
- weight
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired
Links
- 238000000034 method Methods 0.000 title abstract 2
- 239000003381 stabilizer Substances 0.000 abstract 13
- 241000596926 Sparaxis Species 0.000 abstract 1
- 230000008878 coupling Effects 0.000 abstract 1
- 238000010168 coupling process Methods 0.000 abstract 1
- 238000005859 coupling reaction Methods 0.000 abstract 1
- 230000000452 restraining effect Effects 0.000 abstract 1
- 125000006850 spacer group Chemical group 0.000 abstract 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/82—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft
- B64C2027/8263—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft comprising in addition rudders, tails, fins, or the like
- B64C2027/8281—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft comprising in addition rudders, tails, fins, or the like comprising horizontal tail planes
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Toys (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
- Vibration Prevention Devices (AREA)
- Soil Working Implements (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
1328540 Improving longitudinal stability SOC NATIONALE INDUSTRIELLE AEROSPATIALE 20 Nov 1970 [27 Nov 1969] 55284/70 Headings B7G and B7W A method of improving the longitudinal stability of a helicopter H is characterized in that any incipient longitudinal divergence of the helicopter is compensated by creating an opposing moment generated by an inertiaactuated stabilizer E located at the tail end of the helicopter. The stabilizer E pivotable by the inertia of a weight 12 attached indirectly thereto generates a compensating moment which when equilibrated determines a new stabilizer position having a modified lift value which generates a further moment to counteract the initial divergence. Stabilizer E is bolted on to a channel shaped support 4 forming a lever arm, and having two depending flanges 13, 14 and a weight 12. Spaced vertical flanges 17, 18 having openings 19 (20) form an intermediate member within support 4 through which the stabilizer is connected to a vertical stabilizer D by hinge pin 21 and a bell crank 25 depends from flange 18 and is adjustably mounted for setting the equilibrium position of the stabilizer E, in a slotted bracket 30 also secured to stabilizer D. Flanges 13, 14 and 17 18 are differently spaced through hinge pins 45, 46 and 43, 44. A return spring 37 limiting the moment generated, extends between stabilizer 10 and a spacer pin 39 between flanges 13, 14. Vertical flanges 17, 18 are hingedly connected to divergent links 41, 42 through pins 43, 44 the links forming part of the coupling between the stabilizers D and E. A stabilizer damper is also located between flanges 17, (18). Before operation while the helicopter is grounded support 4 is set in an equilibrium position corresponding to the degree of weight attached to the lever arm, a restraining peg (58) Fig. 3 (not shown) is then removed to allow inflight operation. In an alternative embodiment Fig. 10 (not shown) the device is mounted on a tail boom with two half stabilizers 66 projecting one from each channel section 68 located one on each side of the boom and pivotable on a common spar axis 85. The rear end of section 68 carries a weight 69 and the front carries a spring 69a extending down to a transverse arm 77 pivotable on a clevis (78) Fig. 13 (not shown) on the helicopter centre line; the section 68 is pivotable at its front between two brackets 82, 83. A damper 70 and associated linkage 72, 73 are also provided. The stabilizers could be provided with additional control surfaces and the device is especially suitable for use in a helicopter having a rotor with flexible blades, devoid of hinges.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR6940879A FR2067224B1 (en) | 1969-11-27 | 1969-11-27 |
Publications (1)
Publication Number | Publication Date |
---|---|
GB1328540A true GB1328540A (en) | 1973-08-30 |
Family
ID=9043708
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB5528470A Expired GB1328540A (en) | 1969-11-27 | 1970-10-20 | Method and devices for the longitudinal stability of helicopters |
Country Status (4)
Country | Link |
---|---|
US (1) | US3717317A (en) |
DE (1) | DE2056730C3 (en) |
FR (1) | FR2067224B1 (en) |
GB (1) | GB1328540A (en) |
Families Citing this family (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3902688A (en) * | 1974-03-15 | 1975-09-02 | Textron Inc | I-tail empennage |
US4247061A (en) * | 1978-07-12 | 1981-01-27 | United Technologies Corporation | Helicopter with stabilator detuned in antisymmetric vibration modes from main rotor wake excitation frequency |
DE3935893A1 (en) * | 1989-10-27 | 1991-05-02 | Messerschmitt Boelkow Blohm | Method of damping dynamic profiles - with damping load characteristics controlled to counteract resonant frequencies |
DE3935925A1 (en) * | 1989-10-27 | 1991-05-16 | Messerschmitt Boelkow Blohm | Flutter damper for aircraft wing - utilises inertia of mass to rotate sub-wing to produce correcting force |
US7644887B2 (en) * | 2007-02-22 | 2010-01-12 | Johnson Edward D | Yaw control system and method |
CN102574570B (en) | 2009-09-17 | 2014-11-12 | 贝尔直升机泰克斯特龙公司 | Removable horizontal stabilizer for helicopter |
EP2899118B1 (en) * | 2014-01-27 | 2019-01-16 | AIRBUS HELICOPTERS DEUTSCHLAND GmbH | Rotorcraft with a fuselage and at least one main rotor |
FR3035979B1 (en) | 2015-05-05 | 2018-08-17 | Airbus Helicopters | ADVANCED ORDERING ACT FOR STRETCHABLE LOADING |
US11230392B2 (en) | 2019-12-10 | 2022-01-25 | James D Gaston | Apache helicopter stabilizer bearing replacement kit |
US11498136B1 (en) | 2020-08-12 | 2022-11-15 | James D Gaston | Black Hawk bushing removal and reamer device |
Family Cites Families (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2630985A (en) * | 1950-12-07 | 1953-03-10 | United Aircraft Corp | Helicopter stabilizer |
US2941792A (en) * | 1957-06-03 | 1960-06-21 | United Aircraft Corp | Aircraft flight path stabilizer |
US3081052A (en) * | 1957-06-03 | 1963-03-12 | United Aircraft Corp | Variable stabilizing means |
US3027948A (en) * | 1958-01-24 | 1962-04-03 | Kellett Aircraft Corp | Stabilization of rotary wing aircraft |
-
1969
- 1969-11-27 FR FR6940879A patent/FR2067224B1/fr not_active Expired
-
1970
- 1970-10-20 GB GB5528470A patent/GB1328540A/en not_active Expired
- 1970-11-18 DE DE2056730A patent/DE2056730C3/en not_active Expired
- 1970-11-25 US US00092631A patent/US3717317A/en not_active Expired - Lifetime
Also Published As
Publication number | Publication date |
---|---|
DE2056730B2 (en) | 1978-11-30 |
FR2067224A1 (en) | 1971-08-20 |
DE2056730A1 (en) | 1971-06-03 |
DE2056730C3 (en) | 1979-08-02 |
FR2067224B1 (en) | 1974-05-24 |
US3717317A (en) | 1973-02-20 |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
PS | Patent sealed [section 19, patents act 1949] | ||
PCNP | Patent ceased through non-payment of renewal fee |